WO2012173542A1 - Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef - Google Patents

Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef Download PDF

Info

Publication number
WO2012173542A1
WO2012173542A1 PCT/SE2011/050762 SE2011050762W WO2012173542A1 WO 2012173542 A1 WO2012173542 A1 WO 2012173542A1 SE 2011050762 W SE2011050762 W SE 2011050762W WO 2012173542 A1 WO2012173542 A1 WO 2012173542A1
Authority
WO
WIPO (PCT)
Prior art keywords
cover
structural portion
gap
cover according
curvature
Prior art date
Application number
PCT/SE2011/050762
Other languages
English (en)
Inventor
Jakob Bjerkemo
Original Assignee
Saab Ab
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Saab Ab filed Critical Saab Ab
Priority to US14/126,790 priority Critical patent/US20140131513A1/en
Priority to CN201180071637.4A priority patent/CN103596840A/zh
Priority to BR112013030073A priority patent/BR112013030073A2/pt
Priority to ES11867841.6T priority patent/ES2602122T3/es
Priority to PCT/SE2011/050762 priority patent/WO2012173542A1/fr
Priority to EP11867841.6A priority patent/EP2720940B1/fr
Publication of WO2012173542A1 publication Critical patent/WO2012173542A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/001—Devices not provided for in the groups B64C25/02 - B64C25/68
    • B64C2025/003—Means for reducing landing gear noise, or turbulent flow around it, e.g. landing gear doors used as deflectors

Definitions

  • a double-curved cover for covering a gap between two structural portions of an aircraft
  • the present invention relates to a cover for covering a gap between a first structural portion and a second structural portion of an aerial vehicle, according to the preamble of claim 1.
  • An aerial vehicle during flight generates radar echoes to a radar sensing threats who try to detect the vehicle.
  • Such source for generating a radar echo could be a gap between a wing and the vehicle's movable control surface, such as an aileron surface, or a gap between the fuselage skin and a service hatch, etc.
  • the aerial vehicle could be a military aircraft, a helicopter, an unmanned aerial vehicle, a missile etc.
  • the modern aerial vehicle includes often double-curved outer surfaces or aerodynamic surfaces.
  • US 5 695 154 describes a gap filler including a horizontal portion extending across the gap and vertical portions biased into frictional engagement with side walls of the gap, the material of the gap filler is made with electrical conductance for rendering the aircraft less detectable by radar and more capable of discharging lightning.
  • the cover has a first attachment section and a second elastic section which covers the gap.
  • the cover provides a biasing effect for producing a close fit between the movable control surface and the wing.
  • An object is also to eliminate drawbacks of known techniques, develop them and improve the prior art covers for aerial vehicles.
  • the cover will form a close fit onto the skin surface of the aerial vehicle. This is made by the intrinsic biasing force generated by the undulating shape when the flexible section is hold down towards the skin surface of the second structural portion.
  • the hold down action is reached by an attachment of the cover to the first structural portion in a way so that the abutment portion springs against the second structural portion.
  • This biasing force will prevail even if the second structural portion moves in a direction away from the cover, whereby the cover's abutment portion springs towards the second structural portion due to the undulating form and the flexible property of the flexible section including the abutment portion.
  • the cover provides a close fit also when the curvature of the surface of the second structural portion is double-curved.
  • a plain prior art cover would not provide a close fit onto a double-curved skin.
  • a positive effect of the close fit is that a radar sensing threat will have difficulty to detect the aerial vehicle (an aerial vehicle often has a plurality of double-curved surfaces) due to the proper covering of gaps.
  • the desired biasing force can be achieved in direction and force by means of proper shaping of the undulating form.
  • a smaller radius of the double-curvature in some cases requires larger amplitude of the waves and vice versa, etc.
  • the cover is also cost-effective to produce due to its simplicity in design (sheet with undulated section) and provides a low weight, which is desirable for aerial vehicles.
  • the first attachment section also includes an abutment portion having troughs and crests.
  • This second abutment portion can have an undulated form or have a plain surface, depending upon the desire of having a biasing property of said abutment portion.
  • each trough and crest of the abutment portion are of such curvature radius/radii and extension in said unloaded state that the abutment portion fully engages against the curvature of said second structural portion surface in the operating state.
  • the biasing property of the cover in the loaded state is determined.
  • the biasing property of the cover is determined from the need for the abutment portion to always follow and provide a close fit with the movable second structural portion's surface (such as a control surface), particularly when the control surface is tilted in a direction away from the cover.
  • the first attachment section of the cover is plain.
  • one portion of the cover can be fastened to a plain structural portion or single curved structural portion.
  • a portion of the second flexible section forming an undulating shape includes wave ridges that are arranged in a fan-shaped manner.
  • the first attachment section can be fastened smoothly to a plain surface of the first structural portion.
  • the abutment portion includes a sharp edge for engagement with the structural surface portion in the operating state.
  • the aerial vehicle is less detectable by radar. This is due to the lack of gaps and discontinuities in the aerial vehicle's outer surface.
  • the sharp edge provides a minimal step for providing a smooth transition between a control surface and the cover.
  • the gap is defined between a main surface and a control surface.
  • the troughs of the cover provided for engagement with the surface of a control surface, such as a rudder, elevator, aileron etc., which troughs tend to be flattened out and propagate over the surface pressing down neighbouring crests of the cover towards the control surface to provide a close fit between the cover and the control surface.
  • This pressing down tendency of the crests will by means of the propagating troughs produce a biasing or pre-load property within the cover in a self-contained manner.
  • This biasing or pre-load property or intrinsic biasing effect will help the cover to produce a close fit even if the control surface turns in a direction away from a neutral position of the rudder, elevator, aileron, etc.
  • This means that the cover's abutment portion (or end portion) always will press towards the control surface by the pre-load force of the cover, providing a close fit.
  • the cover is designed as an access panel or opening or closing door.
  • a cover having a smooth fit relative the main surface of a double curved skin surface which cover can be used as a hatch.
  • the cover comprises a conductive material.
  • the first attachment section is removable attachable to the first structural portion by means of a fastening element.
  • the fastening means is arranged under the first attachment section of the cover, to be as smooth as possible from both aerodynamic and electromagnetic point of views.
  • FIGs. l a- l c illustrate a first embodiment of a cover showing the achievement of a close fit
  • FIG. 2 illustrates a second embodiment of a cover
  • FIGs. 3a-3b illustrate the cover in FIGs. l a-l c closer in detail
  • FIGs. 4a-4d illustrate the cross-section A-A taken in FIG. 3a and achieved biasing effect
  • FIGs. 5a-5b illustrate a cross-section B-B of a movable aileron mounted to a wing
  • FIG. 5c illustrates the wing in FIGs. 5a-5b from behind
  • FIGs. 6a-6b illustrate a fourth embodiment of a cover in the shape of a double-curved hatch or access panel
  • FIG. 7 illustrates a first attachment section of a cover according to a fifth embodiment
  • FIGs. 8 and 9 illustrate two examples of aerial vehicles comprising different types of covers.
  • FIGs. l a- l c schematically show a first embodiment of a cover 1 illustrating the principle of achieving a close fit between the cover 1 and a double-curved surface.
  • FIG. l a illustrates the cover 1 for covering a gap 2 between a wing skin 3 and a skin 5 of a movable elevator of an aircraft (not shown).
  • the both skins and the cover 1 are made of fibre reinforced resin.
  • the cover 1 includes a first attachment section 9 which can be fasten to the wing skin 3 by means of glue.
  • the cover 1 further includes a flexible section 1 1 which is adapted to cover the gap 2.
  • An abutment portion 13 of the flexible section 1 1 is adapted to abut against the skin 5 of the movable elevator when the aircraft operates.
  • the abutment portion 13 forms in an unloaded state (FIG. l a) an undulating shape U.
  • the undulating shape U presents troughs 1 5 and crests 17, which extend along a double curved plane.
  • This double curved plane has a curvature corresponding essentially with the curvature of the skin's 5 outer surface 6 within an area of the skin 5 corresponding with the abutment portion 13 during said operation.
  • the troughs 15 are adapted for engagement with the outer surface 6 during the operation in a way such that they tend to flatten out and propagate over the outer surface 6 within the area of the skin 5 corresponding with the position of the abutment portion 13. As shown by FIG.
  • FIG. l c is shown when the mounting is finished and the cover 1 provides a close fit against the outer surface 6.
  • the outer surface 6 has a double curved curvature and the inner side of the cover 1 also presents a corresponding double curvature in FIG. l c, when the cover 1 has been flatten out (spread out) over the outer surface 6.
  • a biasing force BF generated by the press down action of the crests 17 of the undulating shape (i.e. the undulating shape predetermined for the cover 1 in the unloaded state) will provide a close fit of the cover 1 towards the surface 6.
  • the force BF is created by the tendency of the troughs 15 to spread out over the outer surface 6 due to the double curved shape of the latter, The press down action of the crests 1 7 towards the outer surface 6 generates thus the biasing force BF.
  • FIG. 2 illustrates a second embodiment of a cover 1.
  • a portion of the flexible section 1 1 forms an undulating shape in the unloaded state, includes wave ridges R that are arranged in a fan-shaped manner.
  • the first attachment section 9 can be fasten smoothly to a plain surface of the first structural portion, such as a wing skin 3.
  • the abutment portion In an unloaded state, the abutment portion
  • the wave ridges R are straight.
  • the cover 1 which edge 14 is the main edge meeting the outer surface 6 of the skin 5 of the movable elevator, will have the same length as the edge 16 of the attachment section 9 parallel with the edge 14.
  • the cover 1 due to the undulating shape, the cover 1 being illustrated from above will be projected as it comprises a longer edge 16 of the attachment section 9 than the edge 14.
  • the wave ridges R of the crests 17 and troughs 15 have such orientation within the cover 1 that they smoothly propagate over the double curved outer surface 6 when the cover 1 has been mounted onto the outer double curved surface 6 for reaching the operating state.
  • the double curved curvature of the surface 6 generates a spreading out/propagating/flattening out effect onto the undulating shape by means of the wave ridges R of the troughs 15 meeting the surface 6.
  • the wave ridges R propagate during said mounting until the stretched crests 17 reach the surface 6, whereby a biasing of the cover 1 is achieved due to the hold down force within the area of the first attachment section 9 and the stretched crests 17.
  • the hold down force is achieved by the fastening of the attachment section 9 to the wing skin 3.
  • the crests 17 are stretched towards the surface 6 due to the flattening out tendency (spreading out/propagating) of the troughs 1 5 meeting the surface 6.
  • FIGs. 3a-3b illustrate the cover 1 in FIGs. la-l c closer in detail.
  • Each trough 15 and crest 1 7 of the abutment portion 13 of the cover 1 are of such curvature radius/radii and extension in the unloaded state shown in FIG. 3a, that the abutment portion 13 fully engages against the double curved curvature C of the surface 6 in the operating state as shown in FIG. 3b.
  • the cover's 1 abutment portion 13 and the surface 6.
  • the biasing property of the cover 1 is preferably determined in a way to allow the abutment portion 1 to always follow, and provide a close fit towards, the moving surface 6.
  • FIG. 3a is taken a cross-section A-A through the undulating shape U in the direction orthogonally to the wave ridges extension and along the longitudinal direction of the cover 1.
  • FIG. 4a The cross-section A-A is schematically shown in FIG. 4a.
  • FIG: 4a is shown a mounting stage wherein service personnel (not shown) applies a force F onto the cover 1 in a direction towards a second structural portion 5 (surface 6) comprising the double-curved curvature C.
  • FIG. 4a is illustrated with a broken line a double curved plane DCP along which the undulating shape U of the cover extends in an unloaded state.
  • the double curved plane DCP of the abutment portion 13 of the cover 1 corresponds to the double-curved curvature C of the surface 6.
  • FIG. 4b is schematically illustrated when the cover 1 , during mounting, reach the surface 6.
  • the troughs 15 and crests 17 of the undulating shape U are illustrated with filled points PT and PC respectively for illustrative clarity reason.
  • the troughs 15 come into contact with the surface 6.
  • the troughs 15 will slide outwardly as shown with arrows A, due to pressure with force F onto the crests 17, as shown in FIG. 4c.
  • the cover 1 is mounted to cover the gap (not shown)
  • the troughs 15 are spread out over the surface 6 since they tend to flatten out and propagate over the surface 6 due to the surface's 6 double-curved curvature.
  • the tendency of the troughs 15 to move outwardly (or in any predetermined direction over the surface 6) when the cover has been mounted for reaching the operating state, will result in that the crests 17 will be pulled by the stretching troughs 15 in a direction towards the surface 6 as shown in FIG. 4d.
  • the troughs 1 5 will thus by means of the spreading out effect press the neighbouring crests 1 towards the surface 6 for providing a close fit between the cover 1 and the surface 6, thereby providing an intrinsic biasing force property within the cover 1 , directed in a direction perpendicular to the surface 6 due to the undulating shape of the abutment portion in the unloaded state.
  • the biasing forces BF perpendicular directed towards the surface 6 is schematically illustrated in FIG. 4d.
  • FIGs. 5a-5b schematically illustrate a cross-section B-B of an aileron 21 movable mounted to a wing 23.
  • FIG. 5c illustrates the wing 23 in FIGs. 5a-5b from behind.
  • the aileron 21 tapers with a curvature towards the wing tip 25 of the wing 23.
  • the cross-section B-B is shown that the aileron 21 has a curvature also transverse the tapering curvature in FIG. 5c, i.e. the aileron 21 comprises a double-curved curvature.
  • a gap 2 Between a first structural portion (the wing 23) and the aileron 21 is formed a gap 2.
  • Two covers 1 are mounted over the gap 2 on the underside and the upper side of the wing 23 respectively.
  • the respective trough and crest (not shown) of the abutment portion 13 of the respective cover 1 are of such curvature radius/radii and extension in the unloaded state (not shown) that the abutment portion 13 fully engages against the double curved curvature of the aileron surface 6 in the operating state. Thereby is achieved a close fit between the cover 1 and the aileron 21 .
  • the biasing property of the cover 1 in the loaded state is determined.
  • the biasing property of the cover 1 is determined from the need for the abutment portion to always follow and provide a close fit with the aileron 21. This is beneficially when the aileron surface 6 is tilted in a direction away from the cover 1 as being shown in FIG. 5b. The cover 1 will thus provide a close fit to the aileron surface 6 also when the aircraft operates.
  • FIGs. 6a-6b illustrate a fourth embodiment of a cover 1 in the shape of a double-curved hatch or access panel 25.
  • the first attachment section 9 of the hatch also includes an abutment portion 13a comprising an undulating shape U.
  • the hatch 25 is made of a composite laminate sheet 26 including electrically conductive material.
  • the hatch 25 is mountable to a fuselage skin 27 of a helicopter 29, shown in FIG. 9.
  • the skin 27 of the helicopter has an electrically conductive property as well. Thereby is achieved that detection of the gap 2 by radar is hard to reach. This is due to the eliminating of the radar echo otherwise produced by the gap 2 between the fuselage skin 27 and a prior art hatch.
  • the electrical conductivity of the hatch 25 connects the first and second structural portions 3 ', 5 ' of the fuselage skin 27 on opposite sides of the gap 2, thus decreasing the electrical discontinuities between the both structural portions 3 ', 5 ' and achieving the helicopter 29 less detectable by radar. At the same time is provided that the structural portions 3', 5 ' are more capable of discharging lightning.
  • the composite laminate sheet 26 has an undulating shape U over its total surface.
  • the FIG. 6a shows a cross-section of a double-curved hatch 25 in an unloaded state.
  • the outermost wave 31 comprising a trough 15 and a crest 17, is shown in the FIG. 6a.
  • Fastening elements 33 in the form of springs 35 and holding protrusions 37, are provided for fastening the hatch 25 to the fuselage skin 27, as shown in FIG. 9.
  • FIG. 6b is shown the operative state wherein service personnel (not shown) has mounted the hatch 25 over the gap 2.
  • the undulating shape is now flatten out, and a biasing force BF is created in a way similar to what has been explained above.
  • This intrinsic biasing force BF is generated by the undulating shape, when the abutment portions 13, 13a are held down towards the fuselage skin 27 by the fastening elements 33.
  • a plain prior art hatch without any undulating shape could not provide a close fit onto a double-curved skin, but should wrinkle.
  • a positive effect of the close fit and the smooth surface of the present hatch 25 is that a radar sensing threat would receive no radar echo from the gap 2.
  • the intrinsic biasing force BF is determined in direction and force by means of properly shaping of the undulating form. In such way the hatch 25 can be made as a removable hatch.
  • the abutment portion 13a includes a sharp thin edge 37 for engagement with the fuselage skin 27 in the operating state. By means of the shaip thin edge 37 smoothly engaging the fuselage skin 27 is achieved that the helicopter 29 is less detectable by radar.
  • FIG. 7 illustrates a first attachment section 9 of a cover 1 according to a fifth embodiment.
  • the cover 1 is fastened removable to a first structural portion 3 by means of a screw 37' .
  • the screw 37' is easy to reach sideways after lifting up of the cover 1 .
  • FIGs. 8 illustrates an aircraft 41 comprising a fin 43 to which a rudder 45 is mounted.
  • Two covers 1 are arranged over a gap between the rudder 45 and the fin 43.
  • the shape of the partly undulating cover can be other than the above-mentioned.
  • the whole cover can have an undulating shape to reach the solution solving the problem.
  • the wave ridges of the undulating shape can be curved or straight.
  • the cover can be made of fibre reinforced resin, metall, and other materials.
  • the wave form is positioned preferably along the edge/edges of the cover, and the mid section of the cover is more rigid and smooth than the edge/edges.
  • the fastening of the hatch can be made by hinges, hydraulic mechanism, mechanical interlocks etc. which are common for doors and hatches which can be opened and closed during flight. Most common aircraft hatches are fastened via hinges and/or fastening elemens such as screws or locking handle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Details Of Aerials (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Casings For Electric Apparatus (AREA)

Abstract

La présente invention porte sur un capot pour couvrir un espace (2) entre une première partie structurelle (3, 3') et une seconde partie structurelle (5, 5') d'un véhicule aérien (29, 41), lequel capot (1, 25) comprend une première section d'attachement (9), pouvant être attachée à la première partie structurelle (3, 3'), et une seconde section souple (11) pour couvrir l'espace (2), la seconde section souple (11) comprenant une partie de butée (13) pour buter contre la seconde partie structurelle (5, 5') dans un état fonctionnel. La partie de butée (13), dans un état déchargé, forme une forme ondulée (U) ayant des auges (15) et des crêtes (17) s'étendant le long d'un plan incurvé, dont la courbure correspond essentiellement à la courbure (C) de la surface (6, 7) de la seconde partie structurelle (5, 5'), les auges (15) étant présentes pour une prise avec ladite surface (6, 27) dans ledit état fonctionnel, de telle manière qu'elles tendent à être aplaties et à se propager sur ladite surface (6, 27), pressant vers le bas les crêtes voisines (17) vers ladite surface (6, 27) pour produire une adaptation étroite entre le capot (1, 25) et la seconde partie structurelle (5, 5').
PCT/SE2011/050762 2011-06-16 2011-06-16 Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef WO2012173542A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US14/126,790 US20140131513A1 (en) 2011-06-16 2011-06-16 Double-curved cover for covering a gap between two structural portions of an aircraft
CN201180071637.4A CN103596840A (zh) 2011-06-16 2011-06-16 用于覆盖在飞行器的两个结构部之间的缝隙的双曲覆盖件
BR112013030073A BR112013030073A2 (pt) 2011-06-16 2011-06-16 cobertura para cobrir uma abertura entre duas porções estruturais de um veículo aéreo
ES11867841.6T ES2602122T3 (es) 2011-06-16 2011-06-16 Cubierta de doble curvatura para cubrir un hueco entre dos porciones estructurales de una aeronave
PCT/SE2011/050762 WO2012173542A1 (fr) 2011-06-16 2011-06-16 Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef
EP11867841.6A EP2720940B1 (fr) 2011-06-16 2011-06-16 Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2011/050762 WO2012173542A1 (fr) 2011-06-16 2011-06-16 Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef

Publications (1)

Publication Number Publication Date
WO2012173542A1 true WO2012173542A1 (fr) 2012-12-20

Family

ID=47357332

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2011/050762 WO2012173542A1 (fr) 2011-06-16 2011-06-16 Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef

Country Status (6)

Country Link
US (1) US20140131513A1 (fr)
EP (1) EP2720940B1 (fr)
CN (1) CN103596840A (fr)
BR (1) BR112013030073A2 (fr)
ES (1) ES2602122T3 (fr)
WO (1) WO2012173542A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3446964A1 (fr) * 2017-08-21 2019-02-27 Claverham Limited Fixation de surface de commande

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8985514B2 (en) * 2012-06-20 2015-03-24 The Boeing Company Composite structural panels and aircraft fuselages
US10017239B2 (en) 2015-12-18 2018-07-10 Northrop Grumman Systems Corporation Dynamic conformal aerodynamic seal (CAS) for aircraft control surfaces
DE102016002844B3 (de) * 2016-03-10 2017-08-10 Premium Aerotec Gmbh Strukturbauteil, Verfahren zur Herstellung eines Strukturbauteils, Druckrumpf für ein Fahrzeug mit Strukturbauteil
CN112613117B (zh) * 2020-12-11 2022-08-12 成都飞机工业（集团）有限责任公司 一种航空口盖由展开尺寸向3d快速构建设计方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6027074A (en) * 1997-02-27 2000-02-22 Mcdonnell Douglas Reinforced elastomer panel
US6170781B1 (en) * 1999-01-21 2001-01-09 Northrop Grumman Corporation Door edge gap and radar signature mitigation door seal
US6209824B1 (en) * 1997-09-17 2001-04-03 The Boeing Company Control surface for an aircraft
US20060249627A1 (en) * 2004-12-31 2006-11-09 Martin Hernandez Agustin M Reinforced cover for cut-outs in an aeordynamic contour
EP2147857A1 (fr) * 2008-07-16 2010-01-27 Alenia Aeronautica S.P.A. Elément de structure pour le recouvrement d'une fente allongée sur la surface aerodynamique d'un aeronef
WO2010023475A2 (fr) * 2008-09-01 2010-03-04 Airbus Operations Limited Joint

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4671977A (en) * 1981-11-09 1987-06-09 Berry Don H Method of and template for joining abutting edges of carpets
US4830315A (en) * 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
US4784355A (en) * 1986-11-10 1988-11-15 The United States Of America As Represented By The Secretary Of The Air Force Flap system for short takeoff and landing aircraft
FR2670177B1 (fr) * 1990-12-05 1993-01-22 Snecma Joint d'etancheite entre l'arriere du fuselage d'un avion et les volets exterieurs de son turboreacteur.
FR2728535A1 (fr) * 1994-12-26 1996-06-28 Aerospatiale Aerofrein a fente variable pour voilure d'aeronef
US5695154A (en) * 1995-08-21 1997-12-09 Northrop Grumman Corporation Gap filler device
GB2323576B (en) * 1997-03-26 2001-08-22 British Aerospace Fairing arrangements for aircraft
GB9920318D0 (en) * 1999-08-27 1999-11-03 British Aerospace A fairing arrangement for an aircraft
FR2827028B1 (fr) * 2001-07-06 2003-09-26 Airbus France Aeronef a carenage ventral et joint pour un tel aeronef
US6877695B2 (en) * 2002-12-13 2005-04-12 The Boeing Company Hinge cover integration into door seal edges
FR2859976B1 (fr) * 2003-09-22 2006-12-08 Airbus France Aile d'aeronef comportant au moins un volet deporteur et volet deporteur pour ladite aile
US8084117B2 (en) * 2005-11-29 2011-12-27 Haresh Lalvani Multi-directional and variably expanded sheet material surfaces
GB0807395D0 (en) * 2008-04-23 2008-05-28 Airbus Uk Ltd Flight surface seal
GB201001834D0 (en) * 2010-02-04 2010-03-24 Airbus Operations Ltd Bridging seal

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6027074A (en) * 1997-02-27 2000-02-22 Mcdonnell Douglas Reinforced elastomer panel
US6209824B1 (en) * 1997-09-17 2001-04-03 The Boeing Company Control surface for an aircraft
US6170781B1 (en) * 1999-01-21 2001-01-09 Northrop Grumman Corporation Door edge gap and radar signature mitigation door seal
US20060249627A1 (en) * 2004-12-31 2006-11-09 Martin Hernandez Agustin M Reinforced cover for cut-outs in an aeordynamic contour
EP2147857A1 (fr) * 2008-07-16 2010-01-27 Alenia Aeronautica S.P.A. Elément de structure pour le recouvrement d'une fente allongée sur la surface aerodynamique d'un aeronef
WO2010023475A2 (fr) * 2008-09-01 2010-03-04 Airbus Operations Limited Joint

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2720940A4 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3446964A1 (fr) * 2017-08-21 2019-02-27 Claverham Limited Fixation de surface de commande

Also Published As

Publication number Publication date
US20140131513A1 (en) 2014-05-15
EP2720940A1 (fr) 2014-04-23
ES2602122T3 (es) 2017-02-17
CN103596840A (zh) 2014-02-19
BR112013030073A2 (pt) 2016-09-20
EP2720940B1 (fr) 2016-08-10
EP2720940A4 (fr) 2015-07-01

Similar Documents

Publication Publication Date Title
EP2720940B1 (fr) Capot à double courbure pour couvrir un espace entre deux parties structurelles d'un aéronef
EP1398269B2 (fr) Procédé et dispositif pour influencer l'écoulement de l'air au moyen d'un bord d'attaque à surface flexible
US8511611B2 (en) Slot seal
EP2923943A1 (fr) Joint d'étanchéité de surface de commande de vol
CA2739522A1 (fr) Bec de bord d'attaque monte sur la surface portante d'un avion
EP3233626B1 (fr) Absorbants acoustiques pour pièces de cellule d'aéronef
JP2016030584A (ja) 航空機のアンテナカバー、航空機の部材用カバー、航空機、および航空機用のレインエロージョンブーツ
US9604716B2 (en) Aircraft hinge arranged between a movable panel and a load-bearing structure
CN101618764A (zh) 用于飞行器、尤其是旋翼机的有可逆变形轮廓的气动翼型
US9199721B2 (en) Wing flaps for aircraft and methods for making the same
EP3489133B1 (fr) Volets d'aile d'aéronef comportant des portes de restauration aérodynamique
EP4011761B1 (fr) Ensemble charnière d'aéronef
US11299254B2 (en) Seal plate for an aerodynamic surface
CN107054625B (zh) 具有自适应激波控制凸起的飞行器机翼
US6170781B1 (en) Door edge gap and radar signature mitigation door seal
US10150557B2 (en) Shape-variable gap covering between control surfaces and adjacent structural components on aircrafts
US7204454B2 (en) Aircraft with articulated leading edge of fuselage and wings
RU210693U1 (ru) Механизм управления элероном с гибкой обшивкой крыла
EP4011762B1 (fr) Ensemble charnière d'aéronef
WO2021094169A1 (fr) Ailes d'aéronef ayant des structures mobiles
GB2611031A (en) Cavity acoustic tones suppression
CN117284467A (zh) 无人机隐身前缘及无人机
EP2516257A1 (fr) Ensemble aile muni d'un volet réglable et élément d'habillage pour l'habillage d'un mécanisme de réglage de volet d'une aile
WO2023041893A1 (fr) Suppression de tonalités acoustiques de cavité

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 11867841

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 14126790

Country of ref document: US

REEP Request for entry into the european phase

Ref document number: 2011867841

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2011867841

Country of ref document: EP

REG Reference to national code

Ref country code: BR

Ref legal event code: B01A

Ref document number: 112013030073

Country of ref document: BR

ENP Entry into the national phase

Ref document number: 112013030073

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20131122